公开(公告)号：US20130206915A1

公开(公告)日：2013-08-15

申请号：US13642521

申请日：2011-04-20

Applicant: Jean-Marc (Joseph) Desaulniers

Inventor： Jean-Marc (Joseph) Desaulniers

IPC: B64C29/00

CPC classification number: B64C29/00 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: The invention relates to a vertical take-off and landing gyropendular craft or drone device (FIG. 18) able to move around in the following different physical environments: in the air, on land, at sea, underwater or in outer space, comprising upper and lower propulsion units, equipped with an annular fairing accommodating a certain number of electronically slaved wing or gas-powered drive or propulsion units situated in the continuation of the axis of this device, mounted on 3-D ball-joints at the ends of a certain number of telescopic rods, for example set at 120° apart at the periphery of the platform and orientable about the three axis according to the plane of flight of the multimodal multi-environment craft, a vertebral structure by way of a 3-D articulated central body of solid or hollow cylindrical shape for forming a stabilized function of stabilizing, maintaining the position and heading, and of an inertial rotary disc platform equipped underneath with a cabin of hemispherical shape extending from the vertebral structure, accommodating a payload or a useful application, designed for various fields of application i.e. the sector of defence or civil security, so as to perform functions of search and rescue, exploration, navigation, transport, surveillance and telecommunications infrastructure deployment in free space.

Abstract translation: 本发明涉及能够在以下不同物理环境中移动的垂直起飞和降落式陀飞轮或无人机装置（图18）：在空中，陆地，海上，水下或外部空间中，包括上部 和较低的推进单元，其配备有环形整流罩，其容纳一定数量的电子从动翼或气动驱动或推进装置，其位于该装置的轴线的延续中，安装在三维球形接头 一些数量的伸缩杆，例如在平台的周边处设置为120°，并且可根据多模式多环境飞行器的飞行平面绕三轴定向，通过3-D铰接的椎体结构 用于形成稳定，保持位置和行程的稳定功能的固体或中空圆柱形的中心体，以及配备在下面的惯性旋转盘平台与半球形舱室 形状从脊椎结构延伸，容纳有效载荷或有用的应用，设计用于各种应用领域，即防卫部门或民用安全，以执行搜索和救援，勘探，导航，运输，监视和电信基础设施的功能 部署在自由空间。

公开(公告)号：US08387911B2

公开(公告)日：2013-03-05

申请号：US12179690

申请日：2008-07-25

Applicant: Daniel Ross Collette

Inventor： Daniel Ross Collette

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风扇风扇芯包括框架，附接到发动机，变速箱组件，风扇和多个控制叶片。 框架上的第一表面包括多个连接或电迹线。 多个连接用于可拆卸地附接携带各种有效载荷的各种吊舱。 因此，可以简单地通过将不同的荚移除并附接到固定的车辆核心，使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚附接到框架时，它们增强了车辆的空气动力学。

公开(公告)号：US08162256B2

公开(公告)日：2012-04-24

申请号：US12051552

申请日：2008-03-19

Applicant: Emray R. Goossen ,  Yogendra Y. Sheoran

Inventor： Emray R. Goossen ,  Yogendra Y. Sheoran

IPC: B64F1/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64C2201/208 ,  B64F1/04

Abstract: A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster and a duct configured to direct airflow generated by the thruster includes a capture plate and an extension. The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

Abstract translation: 用于捕获具有推进器和构造成引导由推进器产生的气流的管道的垂直起飞和着陆（VTOL）车辆的发射和捕获系统包括捕获板和延伸部。 捕获板被配置为改变气流并产生吸引到捕获板的管道的力。 延伸部联接到捕获板，并且被构造成至少有利于将VTOL车辆保持抵靠捕获板。

公开(公告)号：US08146854B2

公开(公告)日：2012-04-03

申请号：US12519988

申请日：2008-02-28

Applicant: John M. Lawrence

Inventor： John M. Lawrence

IPC: B64C27/10

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108

Abstract: A rotorcraft having two coaxial, counter-rotating rotors, one proximate to the forward end of the fuselage and one proximate to the aft end of the fuselage, that generate the forces necessary to lift the craft and maneuver it in the air by adjusting the pitch of the rotor blades throughout their rotation, and a method of flying a dual rotor rotorcraft involving taking off in a vertical orientation, climbing vertically, transitioning to generally horizontal flight, flying horizontally, and subsequently repeating the sequence in reverse to land again in a vertical orientation.

Abstract translation: 旋翼飞机具有两个同轴的反向旋转转子，一个靠近机身前端，一个靠近机身的后端，产生提升飞机所需的力，并通过调节俯仰 的转子叶片的旋转方法，以及一种飞行双转子旋翼航空器的方法，其涉及垂直方向起飞，垂直攀升，转变为大体水平飞行，水平飞行，并随后重复该顺序以在垂直方向上重新着陆 方向。

公开(公告)号：US20110114785A1

公开(公告)日：2011-05-19

申请号：US13001938

申请日：2009-07-01

Applicant: Key Nam Choi

Inventor： Key Nam Choi

IPC: B64C27/06 ,  B64C27/54 ,  B64C29/00

CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127

Abstract: Conventional bottom blade type trefoil flight vehicles have composite structures wherein a plurality of pairs of fixing plates, forward/backward adjustment blades, and left and right rotation adjustment blades are separately mounted and adjusted, and thus have difficulties in scouting and surveillance in an indoor area due to the heavy weights and the large volumes of the flight vehicles. Another conventional flight vehicle has drawbacks in that flight in the left and right directions is difficult, and an adjustment blade and a fixing plate are arranged adjacent to each other to cause mutual influences of wind and non-uniformity in the flow of wind. The present invention provides a flight vehicle characterized in that three pairs of fixing plates with fixed pitch propellers and adjustment blades are installed at an angle of 120 degrees. The present invention allows anti-torque, hovering, forward/backward advancing, left and right rotation, and flight in the left and right direction of flight vehicles, and scouting and surveillance in a narrow space. The flight vehicle of the present invention is simple in structure and control, lightweight, and small in size, thereby improving power efficiency.

Abstract translation: 传统的底叶型三叶飞行器具有复合结构，其中多对固定板，前/后调节叶片和左右旋转调节叶片分别安装和调节，因此在室内区域中的侦察和监视困难 由于重型和大量的飞行车辆。 另一种常规的飞行器具有这样的缺点：在左右方向上的飞行是困难的，并且调节叶片和固定板彼此相邻布置以引起风的相互影响和风的不均匀性。 本发明提供一种飞行器车，其特征在于，具有固定俯仰螺旋桨和调整叶片的三对固定板以120度的角度安装。 本发明允许飞行车辆的左右方向的反扭矩，悬停，前进/后退前进，左右旋转和飞行，并且在狭窄的空间中进行侦察和监视。 本发明的飞行器结构简单，重量轻，体积小，提高了电力效率。

公开(公告)号：US20100252690A1

公开(公告)日：2010-10-07

申请号：US12740005

申请日：2008-11-20

Applicant: Inderpal Singh Hothi ,  Jon Robert Stoackley ,  Steven John Stoackley

Inventor： Inderpal Singh Hothi ,  Jon Robert Stoackley ,  Steven John Stoackley

IPC: B64C29/02 ,  B64C19/00

CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088

Abstract: An unmanned aerial vehicle (UAV) in the form of a “tail sitter” flying wing adapted for vertical take off and landing and transitions between flight as a helicopter and wing-borne flight. The vehicle is electrically powered from onboard batteries and equipped with rotors on miniature helicopter rotor heads at the tips of the wing for both lift, during take off and landing, and forward thrust. In planform the wing comprises, to each side of its longitudinal axis, an inner section with swept back leading and trailing edges, and an outer section with a leading edge more perpendicular to the longitudinal axis, being only mildly swept back or substantially unswept, and a swept forward trailing edge.

Abstract translation: 一种无人机（UAV），以“尾巴”飞翼的形式适用于垂直起飞和着陆，并且作为直升机和机翼飞行之间的飞行之间的过渡。 车辆由车载电池供电，并在机翼顶部的微型直升机转子头上配备转子，用于升降机，起飞和着陆期间以及向前推力。 在平面图中，翼片在其纵向轴线的每一侧包括具有扫掠的前缘和后缘的内部部分，并且具有更垂直于纵向轴线的前缘的外部部分仅被轻度地扫掠或基本上不被刮除，以及 前沿后缘。

公开(公告)号：US07762194B2

公开(公告)日：2010-07-27

申请号：US11531200

申请日：2006-09-12

Applicant: Randy L. Gaigler

Inventor： Randy L. Gaigler

IPC: F42B12/58

CPC classification number: B64G1/641 ,  B64C2201/088 ,  F42B12/58

Abstract: An apparatus that provides shock absorption and ejection for a payload that is to be deployed from a launch capsule is disclosed. The payload ejection mechanism comprises a movable housing that houses a resilient member and a shock-damping system. The rapid acceleration of the capsule upon launch causes the movable housing to move, which compresses the resilient member, thereby storing energy. Movement of the housing also provides shock damping behavior. A locking mechanism maintains the compression of the resilient member until the capsule opens to deploy the payload. As the capsule opens, a restraint decouples from the locking mechanism and permits the resilient member to expand. Expansion of the resilient member causes the movable housing to move, thereby propelling the payload away from the capsule.

Abstract translation: 公开了一种为从发射舱部署的有效载荷提供减震和弹射的装置。 有效载荷弹出机构包括容纳弹性构件和减震系统的可动壳体。 胶囊在发射时的快速加速导致可动壳体移动，从而压缩弹性部件，由此储存能量。 房屋的运动也提供减震行为。 锁定机构保持弹性构件的压缩直到胶囊打开以展开有效载荷。 当胶囊打开时，约束件与锁定机构分离并允许弹性部件膨胀。 弹性构件的膨胀使得可移动壳体移动，从而将有效载荷推离胶囊。

公开(公告)号：US20090314882A1

公开(公告)日：2009-12-24

申请号：US11492490

申请日：2006-07-25

Applicant: Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

Inventor： Emray R. Goossen ,  Glen A. Mantych ,  William T. Campbell

IPC: B64F1/04

CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/201

Abstract: A Micro Air-Vehicle (MAV) starting system that provides the combined functions of: packing protection of sensitive vehicle components, a mechanical starting assembly, and a launch pad. The preferred embodiment comprises a container and a container lid with the MAV clamped to the lid. Also disposed on the container lid is a starting assembly. The lid which doubles as a launching pad with the attached MAV is removed from the container, placed on the ground, the MAV is started with the starting mechanism and launched. The arrangement minimizes the physical risk to the operator, minimizes weight of the total MAV system, consumes minimum space in the operators transport system, and eliminates dependence on supply lines for battery replacement or charging.

Abstract translation: 微型飞行器（MAV）启动系统，提供组合功能：敏感车辆部件的包装保护，机械起动组件和发射台。 优选实施例包括容器和容器盖，其中MAV夹在盖上。 还设置在容器盖上的是起动组件。 将附加的MAV作为发射台的盖子从容器中取出，放在地面上，MAV以起动机构启动并启动。 这种布置可最大限度地减少操作人员的身体风险，最大限度地减少总体MAV系统的重量，消耗操作员运输系统的最小空间，并消除对电池更换或充电的电源线的依赖。

公开(公告)号：US07631834B1

公开(公告)日：2009-12-15

申请号：US11737591

申请日：2007-04-19

Applicant: Samuel Alan Johnson ,  William Dennis Burkard ,  Robert H. Mimlitch, III ,  Robert Henry Mimlitch, Jr. ,  David Anthony Norman

Inventor： Samuel Alan Johnson ,  William Dennis Burkard ,  Robert H. Mimlitch, III ,  Robert Henry Mimlitch, Jr. ,  David Anthony Norman

IPC: B64C27/08 ,  B64C29/00 ,  B64C39/00 ,  B64C27/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/148

Abstract: This disclosure involves aerial robots that dispenses conductive filament or systems, methods, and software for support such aerial robots. One remotely powered aerial robot system includes an aerial robot and a power source. The aerial robot comprises a body, a first propeller coupled to the body and operable to provide thrust to the aerial robot, a rotatable spool coupled to the body, and a conductive filament that is dispensed from the spool by rotation of the spool is one direction and retrieved by rotation of the spool in another direction. The power source is coupled with, and remote from, the aerial robot via the conductive filament, where the conductive filament is operable to power the first propeller using power from the power source.

Abstract translation: 本公开涉及分配用于支持这种空中机器人的导电细丝或系统，方法和软件的空中机器人。 一个远程供电的空中机器人系统包括空中机器人和电源。 空中机器人包括主体，第一螺旋桨，其联接到主体并且可操作以向空中机器人提供推力，联接到主体的可旋转的卷轴，以及通过卷轴的旋转从卷轴分配的导电细丝是一个方向 并通过在另一方向上的线轴的旋转来取回。 电源通过导电细丝与天线机器人耦合并远离，其中导电细丝可操作以使用来自电源的功率为第一螺旋桨供电。

公开(公告)号：US20090045295A1

公开(公告)日：2009-02-19

申请号：US11838731

申请日：2007-08-14

Applicant: Gert Lundgren

Inventor： Gert Lundgren

IPC: G05D1/08 ,  B64C27/22

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/165

Abstract: A vertical/short take-off and landing aircraft with a single proprotor assembly that has a pair of inline counter-rotating rotors. Two inline counter-rotating engines are directly connected to the rotors. One engine is shut down in horizontal flight to improve efficiency. Gimbal mounting the proprotor assembly permits thrust to be directed forward to back and left to right to control pitch and roll when hovering. Varying the relative engine speeds controls yaw. The aircraft is adaptable as an unmanned vehicle.

Abstract translation: 具有单个推进器组件的垂直/短距起飞和着陆飞机，其具有一对在线的反向旋转的转子。 两个直列反向旋转发动机直接连接到转子上。 一个引擎在水平飞行中关闭以提高效率。 安装推进器组件的万向节允许推动力向前指向前向左并向左转，以便在悬停时控制俯仰和滚动。 改变相对发动机转速来控制偏航。 该飞机适用于无人驾驶的车辆。